摘要
由分析固体火箭发动机的高频不稳定燃烧的振幅和频率变化的复杂性开始，通过调整参数，得到在燃烧前期（即振荡燃烧的诱发期）呈现较单纯频率的振荡燃烧。利用中止燃烧试验，得到反映前期振荡燃烧的速度幅分布的烧去肉厚分布．从而由实验证明了：实际的固体火箭发动机中的振荡燃烧诱发期的主频率，并不是基频，而是高次谐波的纵向振荡。又通过内弹道计算分析，建立了不稳定燃烧＂速度耦合＂的理论模型。
The research started from analyzing amplitude and frequency changes ofhigh-frequency unstable combustion in the solid rocket motors,and simple-frequency vibration combustion characteristics in the primary period of combustion were obtained byadjusting parameters of the solid rocket motor.A profile of burned web,which indicatesthe velocity amplitude distribution of vibration combustion in primary period,was alsoacquired by tests with combustion interruption.These demonstrated that the main frequency in inducing period of vibrant combustion of the actual solid rocket motor was thelongitudinal vibration of high-order harmonic instead of fundamental frequency.Thenthe velocity coapling model of unstable combustion was set up through analysis and calculation of the interior ballistics.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1995年第6期1-10,共10页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
燃烧稳定性
振荡燃烧
Solid propellant rocket engine,Combustion stability,Vibrationalcombustion, Erosive burning
